Method for refined attitude control based on output feedback for flexible spacecraft

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United States of America Patent

PATENT NO 9776741
SERIAL NO

15371579

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Abstract

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The present invention provides a method for refined attitude control based on output feedback for a flexible spacecraft. The control method comprises the following steps of: a) building a flexible spacecraft dynamical system Σ1, converting the flexible spacecraft dynamical system Σ1 into a flexible spacecraft dynamical system Σ2, and incorporating spacecraft rigid-flexible coupling dynamic disturbance into the flexible spacecraft dynamical system Σ2; b) constructing an external system Σ3, and describing the rigid-flexible coupling dynamic disturbance through the external system Σ3; c) configuring a disturbance observer for estimating the value of the rigid-flexible coupling dynamic disturbance; d) configuring a dynamic output feedback H∞ controller; e) compounding the disturbance observer in step c) with the dynamic output feedback H∞ controller in step d) to obtain a flexible spacecraft refined attitude control system Σ6; the flexible spacecraft refined attitude control system Σ6 compensating for the rigid-flexible coupling dynamic disturbance through the estimated value.

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Patent Owner(s)

Patent OwnerAddress
BEIHANG UNIVERSITY100191 NO 37 HAIDIAN DISTRICT BEIJING XUEYUAN ROAD BEIJING CITY BEIJING CITY 100191

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Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Guo, Lei Beijing, CN 264 1743
Qiao, Jianzhong Beijing, CN 4 1
Zhang, Dafa Beijing, CN 1 0
Zhang, Peixi Beijing, CN 4 1
Zhang, Ran Beijing, CN 87 332

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